67048 Federal Register / Vol. 79, No. 218 / Wednesday, November 12, 2014 / Rules and Regulations 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2014–0289; Directorate 

Identifier 2013–NM–146–AD; Amendment 

39–18016; AD 2014–22–11] 

RIN 2120–AA64 

Airworthiness Directives; the Boeing 

Company Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are superseding 

Airworthiness Directive (AD) 2012–13– 

08 for certain the Boeing Company 

Model 747–100, 747–100B, 747–200B, 

747–200C, 747–200F, 747–400F, 747SR, 

and 747SP series airplanes, without a 

stretched upper deck or stretched upper 

deck modification. AD 2012–13–08 

required inspections of tension ties and 

surrounding structure for cracking, and 

related investigative and corrective 

actions if necessary; modification of 

tension tie structure or tension tie and 

frame structure at specified stations; and 

post-modification inspections of some 

modified and unmodified areas, and 

repair if necessary. This new AD adds 

inspections in unmodified center 

section tension ties, and repair if 

necessary; post-modification 

inspections of modified and unmodified 

areas, and repair if necessary; a new 

modification of tension tie and frame 

structures; and inspections of tension 

ties and surrounding structure, and 

related investigative and corrective 

actions if necessary. This new AD 

reduces an inspection interval. This AD 

was prompted by widespread fatigue 

damage analysis that resulted in a 

determination that more inspections are 

necessary. We are issuing this AD to 

prevent tension ties from becoming 

severed or disconnected from the 

frames, which could lead to reduced 

structural integrity and sudden 

decompression of the airplane in flight. 

DATES: This AD is effective December 

17, 2014. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of December 17, 2014. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain other publication listed in 

this AD as of August 14, 2012 (77 FR 

40481, July 10, 2012). 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain other publication listed in 

this AD as of February 16, 2006 (71 FR 

1947, January 12, 2006). 

ADDRESSES: For service information 

identified in this AD, contact Boeing 

Commercial Airplanes, Attention: Data 

& Services Management, P. O. Box 3707, 

MC 2H–65, Seattle, WA 98124–2207; 

telephone 206–544–5000, extension 1; 

fax 206–766–5680; Internet https://

www.myboeingfleet.com. You may view 

this referenced service information at 

the FAA, Transport Airplane 

Directorate, 1601 Lind Avenue SW., 

Renton, WA. For information on the 

availability of this material at the FAA, 

call 425–227–1221. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http://

www.regulations.govby searching for 

and locating Docket No. FAA–2014– 

0289; or in person at the Docket 

Management Facility between 9 a.m. 

and 5 p.m., Monday through Friday, 

except Federal holidays. The AD docket 

contains this AD, the regulatory 

evaluation, any comments received, and 

other information. The address for the 

Docket Office (phone: 800–647–5527) is 

Docket Management Facility, U.S. 

Department of Transportation, Docket 

Operations, M–30, West Building 

Ground Floor, Room W12–140, 1200 

New Jersey Avenue SE., Washington, 

DC 20590. 

FOR FURTHER INFORMATION CONTACT: 

Nathan Weigand, Aerospace Engineer, 

Airframe Branch, ANM–120S, Seattle 

Aircraft Certification Office (ACO), 

FAA, 1601 Lind Avenue SW., Renton, 

WA 98057–3356; phone: 425–917–6428; 

fax: 425–917–6590; email: 

Nathan.P.Weigand@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to supersede AD 2012–13–08, 

Amendment 39–17110 (77 FR 40481, 

July 10, 2012). AD 2012–13–08 applied 

to certain The Boeing Company Model 

747–100, 747–100B, 747–200B, 747– 

200C, 747–200F, 747–400F, 747SR, and 

747SP series airplanes, without a 

stretched upper deck or stretched upper 

deck modification. The NPRM 

published in the Federal Register on 

May 29, 2014 (79 FR 30756). The NPRM 

was prompted by a widespread fatigue 

damage analysis conducted by Boeing 

that resulted in a determination that 

additional inspections are needed. The 

NPRM proposed to continue to require 

repetitive inspections of tension ties and 

surrounding structure for cracking, 

additional inspections for certain 

airplanes, and related investigative and 

corrective actions if necessary. The 

NPRM also proposed to continue to 

require modification of tension tie 

structure or tension tie and frame 

structure at specified stations, a postmodification inspection of any modified 

area for cracking, repetitive inspections 

for cracking in the unmodified areas of 

the tension tie structure and frame 

structure at certain stations, and repair 

if necessary. The NPRM proposed to 

add, for certain airplanes, surface HFEC 

inspections for cracking in unmodified 

center section tension ties, and repair if 

necessary; repetitive post-modification 

eddy current inspections for cracking of 

modified and unmodified areas, and 

repair if necessary; a new modification 

(replacement) of tension tie and frame 

structures; and repetitive inspections of 

tension ties and surrounding structure 

for cracking, and related investigative 

and corrective actions if necessary. The 

NPRM also proposed to reduce an 

inspection interval. We are issuing this 

AD to prevent tension ties from 

becoming severed or disconnected from 

the frames, which could lead to reduced 

structural integrity and sudden 

decompression of the airplane in flight. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

have considered the comment received. 

Boeing stated that it concurred with the 

contents of the NPRM (79 FR 30756, 

May 29, 2014). 

Conclusion 

We reviewed the relevant data, 

considered the comments received, and 

determined that air safety and the 

public interest require adopting this AD 

as proposed except for minor editorial 

changes. We have determined that these 

minor changes: 

• Are consistent with the intent that 

was proposed in the NPRM (79 FR 

30756, May 29, 2014) for correcting the 

unsafe condition; and 

• Do not add any additional burden 

upon the public than was already 

proposed in the NPRM (79 FR 30756, 

May 29, 2014). 

Costs of Compliance 

We estimate that this AD affects 86 

airplanes of U.S. registry. 

We estimate the following costs to 

comply with this AD: 


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Federal Register / Vol. 79, No. 218 / Wednesday, November 12, 2014 / Rules and Regulations 67049 

ESTIMATED COSTS

Action Labor cost Parts cost Cost per product Cost on U.S. operators 

Inspection (retained from 

AD 2012–13–08, 

Amendment 39–17110 

(77 FR 40481, July 10, 

2012)).

8 work-hours per tension 

tie location, between 8 

and 12 tension tie locations per airplane, depending on airplane configuration × $85 per hour 

= between $5,440 and 

$8,160.

$0 ...................................... Between $5,440 and 

$8,160 per inspection 

cycle.

Between $467,840 and 

$701,760, per inspection 

cycle. 

One-time inspection for 

Group 2 airplanes, (retained from AD 2012– 

13–08, Amendment 39– 

17110 (77 FR 40481, 

July 10, 2012)).

6 work-hours × $85 per 

hour = $510.

None .................................. $510 .................................. $43,860. 

Modification (retained from 

AD 2012–13–08, 

Amendment 39–17110 

(77 FR 40481, July 10, 

2012)).

Between 24 and 130 workhours, depending on 

station location × $85 

per hour = between 

$2,040 and 11,050.

Between $18,657 and 

$658,423.

Between $20,697 and 

$669,473.

Between $1,779,942 and 

$57,574,678. 

Inspection for unmodified 

area (retained from AD 

2012–13–08, Amendment 39–17110 (77 FR 

40481, July 10, 2012)).

2 work-hours per tension 

tie location, between 8 

and 12 tension tie locations per airplane, depending on airplane configuration × $85 per hour 

= between $1,360 and 

$2,040.

None .................................. Between $1,360 and 

$2,040, per inspection 

cycle.

Between $116,960 and 

$175,440. 

Inspection for modified 

area (retained from AD 

2012–13–08, Amendment 39–17110 (77 FR 

40481, July 10, 2012)).

2 work-hours per tension 

tie location, between 8 

and 12 tension tie locations per airplane, depending on airplane configuration × $85 per hour 

= between $1,360 and 

$2,040.

None .................................. Between $1,360 and 

$2,040.

Between $116,960 and 

$175,440. 

Modification (new action; 1 

U.S. -registered airplane).

Up to 387 work-hours, depending on station location × $85 per hour = up 

to $32,895.

Up to $658,423 ................. Up to $691,318 ................. Up to $691,318. 

Post-modification eddy current inspection of all 

areas (new action).

18 work-hours × $85 per 

hour = $1,530 for each 

tension tie.

None .................................. $1,530 for each tension 

tie, per inspection cycle.

$131,580 for each tension 

tie, per inspection cycle. 

Surface high frequency 

eddy current inspection 

of unmodified tension tie 

center sections (new action).

Up to 120 work-hours, depending on airplane configuration × $85 per hour 

= Up to $10,200.

None .................................. Up to $10,200 ................... Up to $877,200. 

We have received no definitive data 

that would enable us to provide cost 

estimates for the on-condition actions 

specified in this AD. 

Authority for This Rulemaking 

Title 49 of the United States Code 

specifies the FAA’s authority to issue 

rules on aviation safety. Subtitle I, 

Section 106, describes the authority of 

the FAA Administrator. Subtitle VII, 

Aviation Programs, describes in more 

detail the scope of the Agency’s 

authority. 

We are issuing this rulemaking under 

the authority described in Subtitle VII, 

Part A, Subpart III, Section 44701, 

‘‘General requirements.’’ Under that 

section, Congress charges the FAA with 

promoting safe flight of civil aircraft in 

air commerce by prescribing regulations 

for practices, methods, and procedures 

the Administrator finds necessary for 

safety in air commerce. This regulation 

is within the scope of that authority 

because it addresses an unsafe condition 

that is likely to exist or develop on 

products identified in this rulemaking 

action. 

Regulatory Findings 

We have determined that this AD will 

not have federalism implications under 

Executive Order 13132. This AD will 

not have a substantial direct effect on 

the States, on the relationship between 

the national government and the States, 

or on the distribution of power and 

responsibilities among the various 

levels of government. 

For the reasons discussed above, I 

certify that this AD: 

(1) Is not a ‘‘significant regulatory 

action’’ under Executive Order 12866, 

(2) Is not a ‘‘significant rule’’ under 

DOT Regulatory Policies and Procedures 

(44 FR 11034, February 26, 1979), 

(3) Will not affect intrastate aviation 

in Alaska, and 

(4) Will not have a significant 

economic impact, positive or negative, 

on a substantial number of small entities 

under the criteria of the Regulatory 

Flexibility Act. 

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Incorporation by reference, 

Safety. 


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67050 Federal Register / Vol. 79, No. 218 / Wednesday, November 12, 2014 / Rules and Regulations 

Adoption of the Amendment 

Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA amends 14 CFR part 39 as 

follows: 

PART 39—AIRWORTHINESS 

DIRECTIVES 

■ 1. The authority citation for part 39 

continues to read as follows: 

Authority: 49 U.S.C. 106(g), 40113, 44701. 

§ 39.13 [Amended] 

■ 2. The FAA amends § 39.13 by 

removing Airworthiness Directive (AD) 

2012–13–08, Amendment 39–17110 (77 

FR 40481, July 10, 2012), and adding the 

following new AD: 

2014–22–11 The Boeing Company: 

Amendment 39–18016; Docket No. 

FAA–2014–0289; Directorate Identifier 

2013–NM–146–AD. 

(a) Effective Date 

This AD is effective December 17, 2014. 

(b) Affected ADs 

This AD replaces AD 2012–13–08, 

Amendment 39–17110 (77 FR 40481, July 10, 

2012). 

(c) Applicability 

This AD applies to The Boeing Company 

Model 747–100, 747–100B, 747–200B, 747– 

200C, 747–200F, 747–400F, 747SR, and 

747SP series airplanes, certificated in any 

category, as identified in Boeing Alert 

Service Bulletin 747–53A2502, Revision 1, 

dated June 17, 2010. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 53, Fuselage. 

(e) Unsafe Condition 

This AD was prompted by an analysis by 

the manufacturer indicating that tension ties 

are susceptible to widespread fatigue 

damage. The actions were developed to 

support the airplane’s limit of validity of the 

engineering data that support the established 

structural maintenance program. We are 

issuing this AD to prevent tension ties from 

becoming severed or disconnected from the 

frames, which could lead to reduced 

structural integrity and sudden 

decompression of the airplane in flight. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Retained Actions for Group 1 and Groups 

3 Through 6 Airplanes 

This paragraph restates the requirements of 

paragraph (g) of AD 2012–13–08, 

Amendment 39–17110 (77 FR 40481, July 10, 

2012). For Group 1, and Groups 3 through 6 

airplanes identified in Boeing Special 

Attention Service Bulletin 747–53–2502, 

dated April 21, 2005: At the applicable time 

in paragraph (g)(1) or (g)(2) of this AD, do 

detailed and high frequency eddy current 

(HFEC) inspections for cracking of each 

affected tension tie and of the surrounding 

structure. If any cracking is found: Before 

further flight, do all applicable corrective and 

related investigative actions. Do all actions in 

accordance with the Accomplishment 

Instructions of Boeing Special Attention 

Service Bulletin 747–53–2502, dated April 

21, 2005; or Boeing Alert Service Bulletin 

747–53A2502, Revision 1, dated June 17, 

2010. Where Boeing Special Attention 

Service Bulletin 747–53–2502, dated April 

21, 2005; or Boeing Alert Service Bulletin 

747–53A2502, Revision 1, dated June 17, 

2010; specifies to contact Boeing for repair 

instructions: Before further flight, repair the 

area using a method approved in accordance 

with the procedures specified in paragraph 

(n) of this AD. As of August 14, 2012 (the 

effective date of AD 2012–13–08), only 

Boeing Alert Service Bulletin 747–53A2502, 

Revision 1, dated June 17, 2010, may be used 

to accomplish the actions required in this 

paragraph. 

(1) For airplanes identified in Boeing 

Special Attention Service Bulletin 747–53– 

2502, dated April 21, 2005, as Groups 1, 3, 

and 6 airplanes: Do the first inspections 

before the accumulation of 20,000 total flight 

cycles, or within 1,000 flight cycles after 

February 16, 2006 (the effective date of AD 

2006–01–07, Amendment 39–14446 (71 FR 

1947, January 12, 2006)), whichever occurs 

later; and repeat the inspections thereafter at 

intervals not to exceed 4,000 flight cycles 

until the modification required by paragraph 

(j) of this AD is accomplished. 

(2) For airplanes identified in Boeing 

Special Attention Service Bulletin 747–53– 

2502, dated April 21, 2005, as Groups 4 and 

5 airplanes: Do the first inspections before 

the accumulation of 17,000 total flight cycles, 

or within 1,000 flight cycles after February 

16, 2006 (the effective date of AD 2006–01– 

07, Amendment 39–14446 (71 FR 1947, 

January 12, 2006)), whichever occurs later; 

and repeat the inspections thereafter at 

intervals not to exceed 3,000 flight cycles 

until the modification required by paragraph 

(j) of this AD is accomplished. 

(h) Retained Inspections for Group 2 

Airplanes 

This paragraph restates the requirements of 

paragraph (h) of AD 2012–13–08, 

Amendment 39–17110 (77 FR 40481, July 10, 

2012). For Group 2 airplanes identified in 

Boeing Alert Service Bulletin 747 53A2502, 

Revision 1, dated June 17, 2010: At the 

applicable times specified in paragraphs 

(h)(1) and (h)(2) of this AD, do detailed and 

HFEC inspections for cracking of each 

affected tension tie and of the surrounding 

structure, in accordance with the 

Accomplishment Instructions of Boeing 

Special Attention Service Bulletin 747–53– 

2502, dated April 21, 2005; or Boeing Alert 

Service Bulletin 747–53A2502, Revision 1, 

dated June 17, 2010. If any cracking is found: 

Before further flight, do all applicable 

corrective and related investigative actions. 

Do all actions in accordance with the 

Accomplishment Instructions of Boeing 

Special Attention Service Bulletin 747–53– 

2502, dated April 21, 2005; or Boeing Alert 

Service Bulletin 747–53A2502, Revision 1, 

dated June 17, 2010. Where Boeing Special 

Attention Service Bulletin 747–53–2502, 

dated April 21, 2005; or Boeing Alert Service 

Bulletin 747–53A2502, Revision 1, dated 

June 17, 2010; specify to contact Boeing for 

repair instructions: Before further flight, 

repair the area using a method approved in 

accordance with the procedures specified in 

paragraph (n) of this AD. As of August 14, 

2012 (the effective date of AD 2012–13–08, 

Amendment 39–17110 (77 FR 40481, July 10, 

2012)), only Boeing Alert Service Bulletin 

747–53A2502, Revision 1, dated June 17, 

2010, may be used to accomplish the actions 

required by this paragraph. Repeat the 

inspections thereafter at intervals not to 

exceed 3,000 flight cycles until the 

modification required by paragraph (j) of this 

AD is accomplished. 

(1) For stations (STA) 780 through 940: 

Before the accumulation of 17,000 total flight 

cycles, or within 1,000 flight cycles after 

February 16, 2006 (the effective date of AD 

2006–01–07, Amendment 39–14446 (71 FR 

1947, January 12, 2006)), whichever occurs 

later. 

(2) For STA 720, 740, and 760: At the 

earlier of the times specified in paragraph 

(h)(2)(i) or (h)(2)(ii) of this AD. 

(i) Before the accumulation of 17,000 total 

flight cycles, or within 1,000 flight cycles 

after February 16, 2006 (the effective date of 

AD 2006–01–07, Amendment 39–14446 (71 

FR 1947, January 12, 2006)), whichever 

occurs later. 

(ii) Before the accumulation of 8,000 total 

flight cycles, or within 1,000 flight cycles 

after August 14, 2012 (the effective date of 

AD 2012–13–08, Amendment 39–17110 (77 

FR 40481, July 10, 2012)), whichever occurs 

later. 

(i) Retained One-Time Inspection for Group 

2 Airplanes 

This paragraph restates the requirements of 

paragraph (i) of AD 2012–13–08, Amendment 

39–17110 (77 FR 40481, July 10, 2012). For 

airplanes identified in Boeing Alert Service 

Bulletin 747–53A2502, Revision 1, dated 

June 17, 2010, as Group 2 airplanes: Before 

the accumulation of 8,000 total flight cycles, 

or within 1,000 flight cycles after August 14, 

2012 (the effective date of AD 2012–13–08), 

whichever occurs later, do a general visual 

inspection for correct configuration, as 

identified in Boeing Alert Service Bulletin 

747–53A2502, Revision 1, dated June 17, 

2010, of each affected tension tie and of the 

surrounding structure, in accordance with 

the Accomplishment Instructions of Boeing 

Alert Service Bulletin 747–53A2502, 

Revision 1, dated June 17, 2010. 

(1) If all tension ties match the correct 

configurations specified in the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 747–53A2502, Revision 1, 

dated June 17, 2010, no further work is 

required by this paragraph. 

(2) If any incorrect configuration is found, 

before further flight, do detailed and open 

fastener-hole HFEC inspections for cracking 

in the tension tie and frame, in accordance 

with the Accomplishment Instructions of 

Boeing Alert Service Bulletin 747–53A2502, 

Revision 1, dated June 17, 2010. 


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(i) If no crack is found during the 

inspections required by paragraph (i)(2) of 

this AD: Before further flight, install the 

correct configuration for the tension ties at 

locations where the incorrect configuration 

was found, in accordance with the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 747–53A2502, Revision 1, 

dated June 17, 2010; except where Boeing 

Alert Service Bulletin 747–53A2502, 

Revision 1, dated June 17, 2010, specifies to 

contact Boeing for installation instructions, 

use a method approved in accordance with 

the procedures specified in paragraph (n) of 

this AD. 

(ii) If any crack is found during the 

inspections required by paragraph (i)(2) of 

this AD, before further flight, do the actions 

specified in paragraphs (i)(2)(ii)(A) and 

(i)(2)(ii)(B) of this AD. 

(A) Repair the crack in accordance with the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 747–53A2502, Revision 1, 

dated June 17, 2010; except where Boeing 

Alert Service Bulletin 747–53A2502, 

Revision 1, dated June 17, 2010, specifies to 

contact Boeing for appropriate action, before 

further flight, repair the crack using a method 

approved in accordance with the procedures 

specified in paragraph (n) of this AD. 

(B) Install the correct configuration for the 

tension ties at locations where the incorrect 

configuration was found, in accordance with 

the Accomplishment Instructions of Boeing 

Alert Service Bulletin 747–53A2502, 

Revision 1, dated June 17, 2010; except 

where Boeing Alert Service Bulletin 747– 

53A2502, Revision 1, dated June 17, 2010, 

specifies to contact Boeing for installation 

instructions, use a method approved in 

accordance with the procedures specified in 

paragraph (n) of this AD. 

(j) New Tension Tie and Frame Modification 

and Inspections 

(1) For Groups 1 through 16, Configuration 

1, airplanes identified in Boeing Alert 

Service Bulletin 747–53A2605, Revision 3, 

dated July 10, 2013: At the applicable 

compliance time specified in table 1 of 

paragraph 1.E., ‘‘Compliance,’’ of Boeing 

Alert Service Bulletin 747–53A2605, 

Revision 3, dated July 10, 2013, except as 

required by paragraph (l)(1) of this AD, do 

tension tie and frame modifications, in 

accordance with Part 1, and surface HFEC 

inspections for cracks, in accordance with 

Part 4, of the Accomplishment Instructions of 

Boeing Alert Service Bulletin 747–53A2605, 

Revision 3, dated July 10, 2013. 

Accomplishment of these modifications 

terminates the repetitive inspections required 

by paragraphs (g) and (h) of this AD. If any 

crack is found, before further flight, repair 

the crack using a method approved in 

accordance with the procedures specified in 

paragraph (n) of this AD. 

(2) For Groups 17 and 18 airplanes 

identified in Boeing Alert Service Bulletin 

747–53A2605, Revision 3, dated July 10, 

2013: At the applicable time specified in 

table 6 or table 7, as applicable, of paragraph 

1.E., ‘‘Compliance,’’ of Boeing Alert Service 

Bulletin 747–53A2605, Revision 3, dated July 

10, 2013, do a tension tie and frame 

modification (replacement of tension ties and 

frame structure), in accordance with Part 5 or 

Part 6, as applicable, of the Accomplishment 

Instructions of Boeing Alert Service Bulletin 

747–53A2605, Revision 3, dated July 10, 

2013. Accomplishment of these 

modifications terminates the repetitive 

inspections required by paragraph (g) of this 

AD. 

(k) New Repetitive Post-Modification 

Detailed Inspections of Unmodified Areas; 

Repetitive Post-Modification HFEC 

Inspections of Modified and Unmodified 

Areas 

(1) For Groups 1 through 16 airplanes 

identified in Boeing Alert Service Bulletin 

747–53A2605, Revision 3, dated July 10, 

2013: At the applicable time specified in 

table 2 or table 3 of paragraph 1.E., 

‘‘Compliance,’’ of Boeing Alert Service 

Bulletin 747–53A2605, Revision 3, dated July 

10, 2013, do a detailed inspection for 

cracking in the unmodified areas of the 

tension ties, in accordance with Part 2 of the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 747–53A2605, Revision 3, 

dated July 10, 2013. If any cracking is found, 

before further flight, repair using a method 

approved in accordance with the procedures 

specified in paragraph (n) of this AD. Repeat 

the detailed inspection thereafter at the 

applicable time specified in table 2 or table 

3 of paragraph 1.E., ‘‘Compliance,’’ of Boeing 

Alert Service Bulletin 747–53A2605, 

Revision 3, dated July 10, 2013. 

(2) For Groups 1 through 16 airplanes 

identified in Boeing Alert Service Bulletin 

747–53A2605, Revision 3, dated July 10, 

2013: At the applicable time specified in 

table 4 of paragraph 1.E., ‘‘Compliance,’’ of 

Boeing Alert Service Bulletin 747–53A2605, 

Revision 3, dated July 10, 2013, do eddy 

current inspections for cracking in all areas 

of the tension ties (modified and 

unmodified), in accordance with Part 3 of the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 747–53A2605, Revision 3, 

dated July 10, 2013. If any cracking is found, 

before further flight, repair using a method 

approved in accordance with the procedures 

specified in paragraph (n) of this AD. Repeat 

the eddy current inspections thereafter at the 

time specified in table 4 of paragraph 1.E., 

‘‘Compliance,’’ of Boeing Alert Service 

Bulletin 747–53A2605, Revision 3, dated July 

10, 2013. 

(3) For Groups 1 through 16, Configuration 

2, airplanes identified in Boeing Alert 

Service Bulletin 747–53A2605, Revision 3, 

dated July 10, 2013: At the applicable time 

specified in table 5 of paragraph 1.E., 

‘‘Compliance,’’ of Boeing Alert Service 

Bulletin 747–53A2605, Revision 3, dated July 

10, 2013, except as provided by paragraph 

(l)(1) of this AD, do surface HFEC inspections 

for cracking in the unmodified tension tie 

center sections, in accordance with Part 4 of 

the Accomplishment Instructions of Boeing 

Alert Service Bulletin 747–53A2605, 

Revision 3, dated July 10, 2013. If any 

cracking is found, before further flight, repair 

using a method approved in accordance with 

the procedures specified in paragraph (n) of 

this AD. If no cracking is found, no further 

action is required until the repetitive 

inspections required by paragraphs (k)(1) and 

(k)(2) begin. 

(4) For Groups 17 and 18 airplanes 

identified in Boeing Alert Service Bulletin 

747–53A2605, Revision 3, dated July 10, 

2013: At the applicable time specified in 

table 6 or table 7 of paragraph 1.E., 

‘‘Compliance,’’ of Boeing Alert Service 

Bulletin 747–53A2605, Revision 3, dated July 

10, 2013, do detailed and HFEC inspections 

of the modified tension tie and frame 

structure for cracking, in accordance with the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 747–53A2502, Revision 1, 

dated June 17, 2010. Except as required by 

paragraph (l)(4) of this AD, if any cracking is 

found, before further flight, repair using a 

method approved in accordance with the 

procedures specified in paragraph (n) of this 

AD. Repeat the detailed and HFEC 

inspections thereafter at the times specified 

in table 6 or table 7, as applicable, of Boeing 

Alert Service Bulletin 747–53A2605, 

Revision 3, dated July 10, 2013. 

(l) Service Information Clarifications and 

Exceptions 

(1) Where paragraph 1.E., ‘‘Compliance,’’ of 

Boeing Alert Service Bulletin 747–53A2605, 

Revision 3, dated July 10, 2013, specifies a 

compliance time ‘‘after the revision 3 date of 

this service bulletin,’’ this AD requires 

compliance within the specified time after 

the effective date of this AD. 

(2) Where Boeing Alert Service Bulletin 

747–53A2605, Revision 3, dated July 10, 

2013, specifies to contact Boeing for repair 

instructions, this AD requires repair before 

further flight using a method approved in 

accordance with the procedures specified in 

paragraph (n) of this AD. 

(3) Boeing Alert Service Bulletin 747– 

53A2605, Revision 3, dated July 10, 2013, 

refers to Section 51–10–02 of the Boeing 747– 

400F Structural Repair Manual (SRM) and 

Section 51–10–01 of the Boeing 747–100/

200/300 SRM as additional sources of 

guidance for removing small cracks and 

fatigue damage material from the existing 

holes in the unmodified center section of the 

tension tie channels. Where those SRM 

sections state that ‘‘zero-timing must only be 

used where specifically permitted in an SRM 

chapter-section-repair,’’ this AD allows the 

zero-timing procedures specified in those 

SRM sections. 

(4) Where Boeing Alert Service Bulletin 

747–53A2605, Revision 3, dated July 10, 

2013, specifies to contact Boeing for repair 

instructions, this AD requires repair before 

further flight using a method approved in 

accordance with the procedures specified in 

paragraph (n) of this AD. 

(m) Credit for Previous Actions 

(1) This paragraph restates the credit 

provided in paragraph (m) of AD 2012–13– 

08, Amendment 39–17110 (77 FR 40481, July 

10, 2012). This paragraph provides credit for 

the actions required by paragraphs (j)(1) 

and(k)(1) of this AD, if those actions were 

performed before August 14, 2012 (the 

effective date of AD 2012–13–08) using 

Boeing Alert Service Bulletin 747–53A2605, 

dated December 8, 2009, which was 

incorporated by reference in AD 2012–13–08. 

(2) For Groups 1 through 16 airplanes 

identified in Boeing Alert Service Bulletin 


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67052 Federal Register / Vol. 79, No. 218 / Wednesday, November 12, 2014 / Rules and Regulations 

747–53A2605, Revision 3, dated July 10, 

2013: This paragraph provides credit for the 

actions required by paragraphs (j)(1) and 

(k)(1) of this AD, if those actions were 

performed before the effective date of this AD 

using Boeing Alert Service Bulletin 747– 

53A2605, Revision 2, dated December 9, 

2011, which is not incorporated by reference 

in this AD. 

(n) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Seattle Aircraft 

Certification Office (ACO), FAA, has the 

authority to approve AMOCs for this AD, if 

requested using the procedures found in 14 

CFR 39.19. In accordance with 14 CFR 39.19, 

send your request to your principal inspector 

or local Flight Standards District Office, as 

appropriate. If sending information directly 

to the manager of the ACO, send it to the 

attention of the person identified in 

paragraph (o)(1) of this AD. Information may 

be emailed to: 9-ANM-Seattle-ACO-AMOCRequests@faa.gov. 

(2) Before using any approved AMOC, 

notify your appropriate principal inspector, 

or lacking a principal inspector, the manager 

of the local flight standards district office/

certificate holding district office. 

(3) An AMOC that provides an acceptable 

level of safety may be used for any repair 

required by this AD if it is approved by the 

Boeing Commercial Airplanes Organization 

Designation Authorization (ODA) that has 

been authorized by the Manager, Seattle 

ACO, to make those findings. For a repair 

method to be approved, the repair must meet 

the certification basis of the airplane. 

(4) AMOCs approved for inspections 

required by AD 2012–13–08, Amendment 

39–17110 (77 FR 40481, July 10, 2012) are 

approved as AMOCs for the corresponding 

inspection provisions of paragraphs (g), (h), 

and (i) of this AD. 

(5) AMOCs approved for AD 2012–13–08, 

Amendment 39–17110 (77 FR 40481, July 10, 

2012) that granted modification deviations 

are approved as AMOCs for the 

corresponding modification required by 

paragraph (j)(1) of this AD. 

(o) Related Information 

(1) For more information about this AD, 

contact Nathan Weigand, Aerospace 

Engineer, Airframe Branch, ANM–120S, 

Seattle Aircraft Certification Office (ACO), 

FAA, 1601 Lind Avenue SW., Renton, WA 

98057–3356; phone: 425–917–6428; fax: 425– 

917–6590; email: Nathan.P.Weigand@

faa.gov. 

(2) Service information identified in this 

AD that is not incorporated by reference is 

available at the addresses specified in 

paragraphs (p)(6) and (p)(7) of this AD. 

(p) Material Incorporated by Reference 

(1) The Director of the Federal Register 

approved the incorporation by reference 

(IBR) of the service information listed in this 

paragraph under 5 U.S.C. 552(a) and 1 CFR 

part 51. 

(2) You must use this service information 

as applicable to do the actions required by 

this AD, unless the AD specifies otherwise. 

(3) The following service information was 

approved for IBR on December 17, 2014. 

(i) Boeing Alert Service Bulletin 747– 

53A2605, Revision 3, dated July 10, 2013. 

(ii) Reserved. 

(4) The following service information was 

approved for IBR on August 14, 2012 (77 FR 

40481, July 10, 2012). 

(i) Boeing Alert Service Bulletin 747– 

53A2502, Revision 1, dated June 17, 2010. 

(ii) Reserved. 

(5) The following service information was 

approved for IBR on February 16, 2006 (71 

FR 1947, January 12, 2006). 

(i) Boeing Special Attention Service 

Bulletin 747–53–2502, dated April 21, 2005. 

(ii) Reserved. 

(6) For service information identified in 

this AD, contact Boeing Commercial 

Airplanes, Attention: Data & Services 

Management, P. O. Box 3707, MC 2H–65, 

Seattle, WA 98124–2207; telephone 206– 

544–5000, extension 1; fax 206–766–5680; 

Internet https://www.myboeingfleet.com. 

(7) You may view this service information 

at FAA, Transport Airplane Directorate, 1601 

Lind Avenue SW., Renton, WA. For 

information on the availability of this 

material at the FAA, call 425–227–1221. 

(8) You may view this service information 

that is incorporated by reference at the 

National Archives and Records 

Administration (NARA). For information on 

the availability of this material at NARA, call 

202–741–6030, or go to: http://

www.archives.gov/federal-register/cfr/ibrlocations.html. 

Issued in Renton, Washington, on October 

28, 2014. 

Jeffrey E. Duven, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2014–26536 Filed 11–10–14; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2014–0430; Directorate 

Identifier 2014–NM–083–AD; Amendment 

39–18014; AD 2014–22–09] 

RIN 2120–AA64 

Airworthiness Directives; the Boeing 

Company Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for all the 

Boeing Company Model 767 airplanes. 

This AD was prompted by a report of a 

rotary actuator for the trailing edge (TE) 

flap that had slipped relative to its 

mating reaction ring, which is attached 

to the flap support rib. This AD requires 

repetitive inspections for corrosion of 

the fixed ring gear and reaction ring 

splines of the rotary actuator assembly 

for each support position, and related 

investigative and corrective actions if 

necessary. We are issuing this AD to 

detect and correct flap rotary actuator 

gear disengagement from its mating 

reaction ring. This disengagement with 

flaps extended could cause an 

uncommanded roll due to flap 

blowback, overload, or flap departure 

from the airplane, which could 

compromise safe flight and landing of 

the airplane. 

DATES: This AD is effective December 

17, 2014. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of December 17, 2014. 

ADDRESSES: For service information 

identified in this AD, contact Boeing 

Commercial Airplanes, Attention: Data 

& Services Management, P. O. Box 3707, 

MC 2H–65, Seattle, WA 98124–2207; 

telephone 206–544–5000, extension 1; 

fax 206–766–5680; Internet https://

www.myboeingfleet.com. You may view 

this referenced service information at 

the FAA, Transport Airplane 

Directorate, 1601 Lind Avenue SW., 

Renton, WA. For information on the 

availability of this material at the FAA, 

call 425–227–1221. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http://

www.regulations.gov by searching for 

and locating Docket No. FAA–2014– 

0430; or in person at the Docket 

Management Facility between 9 a.m. 

and 5 p.m., Monday through Friday, 

except Federal holidays. The AD docket 

contains this AD, the regulatory 

evaluation, any comments received, and 

other information. The address for the 

Docket Office (phone: 800–647–5527) is 

Docket Management Facility, U.S. 

Department of Transportation, Docket 

Operations, M–30, West Building 

Ground Floor, Room W12–140, 1200 

New Jersey Avenue SE., Washington, 

DC 20590. 

FOR FURTHER INFORMATION CONTACT: 

Allen Rauschendorfer, Aerospace 

Engineer, Airframe Branch, ANM–120S, 

FAA, Seattle Aircraft Certification 

Office, 1601 Lind Avenue SW., Renton, 

WA 98057–3356; phone: 425–917–6487; 

fax: 425–917–6590; email: 

Allen.Rauschendorfer@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 by adding an AD that would 

apply to all The Boeing Company Model 

767 airplanes. The NPRM published in 


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